CN105026732A - Compact dosing device for an injector with two fuel circuits for an aircraft turbomachine - Google Patents

Compact dosing device for an injector with two fuel circuits for an aircraft turbomachine Download PDF

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Publication number
CN105026732A
CN105026732A CN201480012251.XA CN201480012251A CN105026732A CN 105026732 A CN105026732 A CN 105026732A CN 201480012251 A CN201480012251 A CN 201480012251A CN 105026732 A CN105026732 A CN 105026732A
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CN
China
Prior art keywords
fuel
opening
seal element
displacement
outlet
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
CN201480012251.XA
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Chinese (zh)
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CN105026732B (en
Inventor
克里斯托弗·柴贝利叶
塞巴斯蒂安·洛瓦尔
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Safran Aircraft Engines SAS
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SNECMA SAS
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Publication of CN105026732A publication Critical patent/CN105026732A/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/22—Fuel supply systems
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/22—Fuel supply systems
    • F02C7/232—Fuel valves; Draining valves or systems
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/26—Control of fuel supply
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/26—Control of fuel supply
    • F02C9/263—Control of fuel supply by means of fuel metering valves
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16K—VALVES; TAPS; COCKS; ACTUATING-FLOATS; DEVICES FOR VENTING OR AERATING
    • F16K11/00—Multiple-way valves, e.g. mixing valves; Pipe fittings incorporating such valves
    • F16K11/02—Multiple-way valves, e.g. mixing valves; Pipe fittings incorporating such valves with all movable sealing faces moving as one unit
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16K—VALVES; TAPS; COCKS; ACTUATING-FLOATS; DEVICES FOR VENTING OR AERATING
    • F16K11/00—Multiple-way valves, e.g. mixing valves; Pipe fittings incorporating such valves
    • F16K11/02—Multiple-way valves, e.g. mixing valves; Pipe fittings incorporating such valves with all movable sealing faces moving as one unit
    • F16K11/06—Multiple-way valves, e.g. mixing valves; Pipe fittings incorporating such valves with all movable sealing faces moving as one unit comprising only sliding valves, i.e. sliding closure elements
    • F16K11/065—Multiple-way valves, e.g. mixing valves; Pipe fittings incorporating such valves with all movable sealing faces moving as one unit comprising only sliding valves, i.e. sliding closure elements with linearly sliding closure members
    • F16K11/07—Multiple-way valves, e.g. mixing valves; Pipe fittings incorporating such valves with all movable sealing faces moving as one unit comprising only sliding valves, i.e. sliding closure elements with linearly sliding closure members with cylindrical slides
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16K—VALVES; TAPS; COCKS; ACTUATING-FLOATS; DEVICES FOR VENTING OR AERATING
    • F16K11/00—Multiple-way valves, e.g. mixing valves; Pipe fittings incorporating such valves
    • F16K11/02—Multiple-way valves, e.g. mixing valves; Pipe fittings incorporating such valves with all movable sealing faces moving as one unit
    • F16K11/06—Multiple-way valves, e.g. mixing valves; Pipe fittings incorporating such valves with all movable sealing faces moving as one unit comprising only sliding valves, i.e. sliding closure elements
    • F16K11/065—Multiple-way valves, e.g. mixing valves; Pipe fittings incorporating such valves with all movable sealing faces moving as one unit comprising only sliding valves, i.e. sliding closure elements with linearly sliding closure members
    • F16K11/07—Multiple-way valves, e.g. mixing valves; Pipe fittings incorporating such valves with all movable sealing faces moving as one unit comprising only sliding valves, i.e. sliding closure elements with linearly sliding closure members with cylindrical slides
    • F16K11/0716—Multiple-way valves, e.g. mixing valves; Pipe fittings incorporating such valves with all movable sealing faces moving as one unit comprising only sliding valves, i.e. sliding closure elements with linearly sliding closure members with cylindrical slides with fluid passages through the valve member
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23K—FEEDING FUEL TO COMBUSTION APPARATUS
    • F23K5/00—Feeding or distributing other fuel to combustion apparatus
    • F23K5/02—Liquid fuel
    • F23K5/14—Details thereof
    • F23K5/147—Valves
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/36—Supply of different fuels
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23N—REGULATING OR CONTROLLING COMBUSTION
    • F23N2235/00—Valves, nozzles or pumps
    • F23N2235/12—Fuel valves
    • F23N2235/16—Fuel valves variable flow or proportional valves
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23N—REGULATING OR CONTROLLING COMBUSTION
    • F23N2235/00—Valves, nozzles or pumps
    • F23N2235/12—Fuel valves
    • F23N2235/24—Valve details
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T137/00—Fluid handling
    • Y10T137/7722—Line condition change responsive valves
    • Y10T137/7837—Direct response valves [i.e., check valve type]
    • Y10T137/7904—Reciprocating valves
    • Y10T137/7922—Spring biased
    • Y10T137/7929—Spring coaxial with valve

Abstract

The invention concerns a fuel dosing device (10) for a fuel injector of an aircraft turbomachine, comprising an opening (24), a movable member (28) for sealing the opening, and elastic return means (60a, 60b), the member being capable of moving under the effect of the fuel pressure. The device (10) comprises a first outlet (10a) communicating with a primary circuit (12) of the injector and a second outlet (10b) communicating with a secondary circuit (14). Moreover, it is designed such that, up to a defined level of displacement of the sealing member, the latter allows the fuel coming from the opening (24) to reach the first outlet (10a) and, only beyond the defined level of displacement, the member allows the fuel coming from the opening (24) to reach the second outlet. The device (10) further comprises a hollow outer body (20), and a hollow intermediate body (22) housed in the outer body (20), said opening (24) being made in said intermediate body provided with a seat (26) for receiving the sealing member (28). The sealing member (28) is housed slidably movable in said intermediate body (22). A fuel flow space (30) is provided between the intermediate and outer bodies (22, 20), the intermediate body being provided with orifices (32) for the fuel to pass from the inside of said intermediate body (22) to said fuel flow space (30), said flow space communicating with said first outlet (10a). A secondary opening (46) for the fuel to pass through is provided on the intermediate body (22), the secondary opening (46) being intended to be sealed by the movable member (28) provided it has not reached said defined level of displacement, and intended to be opened when the movable member (28) is between the defined level of displacement and the maximum opening position of same, said secondary opening (46) communicating with said second outlet (10b).

Description

For the compact dosing device with the sparger of two fuel circuits of aircraft turbine machine
Technical field
The present invention relates to the fuel injector field for aircraft turbine machine, particularly relate to double loop (namely for the primary circuit of small flow and the second servo loop for high flow) fuel injector.
The present invention is applicable to all types of aircraft turbine machine, especially turbo-jet aircraft engine and turbosupercharger.
Background technique
Such as can know double loop fuel injector from file FR2817017.Usually there is cut-off valve, because it can provide the fuel infiltration preventing from being arranged in fuel circuit to the fluid-tight engagement of firing chamber, therefore also referred to as seal valve during engine stop.When the pressure difference of these valve both sides makes this valve be opened, fuel is transported to the primary circuit of sparger on the one hand, is transported to the metering valve of the entrance providing the second servo loop leading to sparger on the other hand.When the fuel pressure difference deltap of metering valve both sides reaches a high value (such as 7 bar), this metering valve allows fuel to pass through.Metering valve regulates the quantity of the fuel being ejected into firing chamber according to the displacement that it depends on pressure difference.
Although this common scheme can satisfy the demands, can improve in disadvantageous interactional risk between gross mass, burden and two valves.
Summary of the invention
In view of this, the object of the invention is to overcome at least in part the above-mentioned defect relating to and realize prior art.
For achieving the above object, the invention provides a kind of quota of fuel equipment of the sparger for aircraft turbine machine, described equipment comprise for fuel picked-up opening, for sealing the moveable element of described opening and being designed to recover the elastic recovery device of described seal element on the direction of the described element operating position at closed described opening place in a sealing manner, described element is designed to be shifted from its operating position under the effect of the fuel pressure being applied to this element.
Described metering equipment comprises first exporting and second exporting of being intended to carry out circulating with the second servo loop of described sparger of being intended to carry out circulating with the primary circuit of described sparger, and described metering equipment is designed to the degree of displacement of the restriction reaching described seal element on the direction of maximum open position, described seal element allows the fuel from described opening to arrive described first outlet.In addition, only exceed the degree of displacement of the described restriction of described element, described seal element just allows the described fuel from described opening to arrive described second outlet.
According to the present invention, described metering equipment comprises:
Hollow ectosome;
Be contained in the hollow intermediate in described ectosome, described opening is configured in the described intermediate of the valve seat had for holding described seal element;
Be contained in the described seal element of movement slidably in described intermediate;
Be provided in the fuel flowing space between described intermediate and ectosome, described intermediate to have for fuel from the inside of this intermediate through the aperture reaching the described fuel flowing space, the described flowing space and described first outlet stream;
Be provided in the second opening passed through for described fuel on described intermediate, if described second opening is intended to not reach the degree of displacement of described restriction just by described moveable component seal, and described second opening is intended to be released when described moveable element is between the degree of displacement of restriction and its maximum open position, described second opening and described second outlet stream.
Special usefulness of the present invention is that it achieves the single movable seal element that can control to supply the elementary of sparger and second servo loop.As for the scheme with two valves of series connection of the prior art, The present invention reduces interaction possible between two valves.The present invention can also reduce the friction between burden, gross mass, the quantity of parts and parts.
Preferably, the parts passed through on the second opening for fuel change according to the relative position of element about this opening.
Preferably, when exceeding the degree of displacement of described restriction of described seal element, described seal element allows the fuel from described opening to arrive described second outlet and described first outlet.Therefore, although other may be had to design, equipment be designed to when second outlet be supplied to time first export by continuation supply fuel.
Preferably, described elastic recovery device comprises at least one first spring and the second spring, described second spring is not initiated (solicited) by the stroke at least partially of arranging as the described seal element the operating position from described seal element, and described first and second springs are arranged as when seal element is when being positioned at the degree of displacement of described restriction, and each spring is caused by seal element.But do not exceeding under protection scope of the present invention prerequisite, other configuration is also possible.Especially, single spring can be limited.But the technological scheme (as described above) with two or more spring considers the larger adjustment amplitude for metering equipment.
Preferably, described first and second springs are arranged concurrently.Described first and second springs are especially located according to the axle (particularly about this axle concentrically) of equipment.
According to additional feature, hardness ratio first spring that described second spring has is large.Or described second spring can be applied in more prestressing force compared with the first spring in operating position.
Preferably, described removable original paper defines cavity, and fuel is intended to transport in cavity to arrive described second outlet.Fuel can also be made on the direction of described second outlet from flows outside to movable seal element.
According to specific embodiment, described second spring is provided between the block of intermediate and supporting part, and movable seal element have to be intended on the direction of its maximum open position only from the degree of displacement of described restriction and the degree of displacement exceeding described restriction to contact the additional supporting part of described supporting part.
Selectively, described second spring is provided between the supporting part of block and moveable element, and movable seal element to have on the direction of the maximum open position at movable seal element only from the degree of displacement of described restriction and the degree of displacement exceeding described restriction carrys out the joint element of engaging support members.
Supporting part especially can cause the second spring according to by institute's applied pressure in the metering equipment of fuel on moveable element in the mode of compression.
Then, after being filled with the unused gap existed between the supporting part and joint element of moveable element at least in part, can by being reached the degree of displacement limited of movable seal element by joint element engaging support members.
In this configuration, supporting part is preferably safety valve.Safety valve is inherently provided for the sealing function of independent or with other combination of elements of moveable element fuel metering equipment.
According to additional feature, movable seal element especially comprises piston and supporting part.
When supporting part has parts (such as the valve rod) that be rectangle, joint element is preferably the groove in piston.Present invention also offers a kind of fuel injector for aircraft turbine machine, described fuel injector comprises at least one metering equipment as above, and described first outlet is circulated with primary circuit, and the second outlet is circulated with the second servo loop of same sparger.
Present invention also offers a kind of aircraft turbine machine firing chamber comprising multiple above-mentioned fuel injector.
Finally, present invention also offers a kind of aircraft turbine machine comprising this firing chamber.
Other usefulness of the present invention and feature are by by providing in following description in detail.
Accompanying drawing explanation
Be described in conjunction with following accompanying drawing, wherein:
Fig. 1 is the diagrammatic view of the fuel injector for turbo machine of the preferred embodiment of the present invention;
Fig. 2 a to Fig. 2 c shows the metering equipment of sparger in Fig. 1 of the first embodiment of the present invention in the difference configuration adopted because fuel pressure difference deltap can increase the weight of between the upstream and downstream of metering equipment in more detailed manner as half cross section;
Fig. 3 a to 3c as cross section show in more detailed manner Fig. 2 a to 2c similar and the metering equipment of the sparger of Fig. 1 in the different configurations adopted because fuel pressure difference deltap can increase the weight of between the upstream and downstream of metering equipment.
Embodiment
Fig. 1 shows the fuel injector 1 for aircraft turbine machine of the preferred embodiment of the present invention.
" multi-mode " type sparger 1 (several supply loop is dual fuel circuit here) is connected to upstream the device (such as storage tank 2) for fuel-in-storage.In its downstream, sparger is according to being the bottom that conventional and known mode passes firing chamber 4 for a person skilled in the art.
Sparger 1 is from upstream to downstream and comprises filter 6, diaphragm 8 and metering equipment 10 generally on the flow direction of fuel through this sparger.The second fuel outlet 10b that equipment 10 comprises the first fuel outlet 10a and separates with the first fuel outlet.First outlet 10a supplies primary fuel loop 12, and the second outlet supplies the second fuel circuit 14, is intended to the flow providing more high flow rate on the direction of firing chamber.Each loop 12,14 is being associated with the cyclone separator 16,17 of the fuel for spraying/putting into rotation close to the downstream end of sparger.
All said elements of sparger are all provided in shell 13, and its housing 13 has the shape of finger or rattan usually.
Fig. 2 a and 3a more specifically shows in detail metering equipment 10 in the closed configuration, and the fuel wherein from storage tank can not penetrate this equipment.
Use multiple coaxial component forming devices 10 with the axle 18 corresponding with the axle of sparger.
First this is the hollow ectosome 20 over much of its length with constant circular cross-section.The hollow ectosome 20 of the first embodiment has tapered narrowing portion 21 in downstream.More generally, ectosome 20 has the tubulose centered by axle 18, and limits the first outlet 10a from outside.
Accommodate hollow intermediate 22 in ectosome 20 inside, use one or the several parts be fixed to one another can construct intermediate 22.In upstream portion, intermediate 22 has the opening 24 centered by axle 18 for absorbing fuel.Near this opening, intermediate 22 defines the valve seat 26 for holding movable seal element 28, and valve seat has O-shape seal ring 29.
Intermediate 22 defines the annular fuel flowing space 30 be provided between this intermediate and ectosome 20.In addition, intermediate to have for fuel from the inside of this intermediate 22 through the aperture 32 arriving flow in fuel and move space 30.These apertures be positioned on the sidewall of intermediate 22 are provided at and allow fuel to enter near the axially open 24 of metering equipment.
In downstream part, intermediate 22 has by using ectosome 20 to limit the first annular fuel outlet 10a in inside, and the shoulder 36 that the pipe portion 38 limiting the second fuel outlet 10b of the circular cross-section centered by axle 18 in outside continues.Therefore, in downstream part, the fuel flowing space 30 and first exports 10a and circulates.
As mentioned above, metering equipment 10 also comprises with the seal element 28 be contained in intermediate 20 along axle 18 slidably movement.
Moveable element 28 has the upstream extremity comprising upstream pressure-bearing surface, and upstream pressure-bearing surface has the shape of bearing plate substantially in a first embodiment, and fuel can apply the power of displacement on the pressure-bearing surface of upstream.Element 28 is hollow, which defines cavity 40, and fuel is intended to carry to arrive the second outlet 10b (detailed description will provide hereinafter) in cavity 40.For this reason, the sidewall of element 28 has the fuel inlet aperture 42 be positioned near bearing plate, and is positioned at the fuel outlet aperture 44 limiting downstream part farther on the same sidewall of cavity 40.
In the downstream part of intermediate 22, the second opening 46 is configured to fuel to be passed through.In the configuration shown in Fig. 2 a and 3a, this opening 46 is sealed with the downstream 50 of the circular cross-section of the shape of opening shape complementation by having of moveable element 28.If needed, seal arrangement can be added.
Between this downstream 50 and fuel outlet aperture 44, movable seal element 28 has the part 54 with narrowing cross section, when movable seal element 28 is positioned at the position relative with the second opening 46, can by make fuel along and this second opening circulate second export the direction of 10b by discharging the second opening 46.Or rather, the second opening 46 leads to the space 56 below the downstream part being positioned at moveable element, and the second outlet 10b is led in this space 56.
In addition, equipment 10 comprises applying and causes element 28 to return to the elastic recovery device of the power of its operating position described in Fig. 2 a, and wherein element 28 extrudes valve seat 26.
Elastic device in the preferred embodiment of Fig. 2 a to 2c and Fig. 3 a to 3c comprises the first spring 60a and the second spring 60b.First spring 60a and the second spring 60b especially locates along the axle 18 of equipment 10 with one heart about this axle 18.
More specifically, with reference to Fig. 2 a to 2c, the shoulder 36 of the first spring 60a mono-aspect extruding intermediate 22, extrudes the downstream of moveable element 28 on the other hand.Second spring 60b extrudes the downstream block 62 of intermediate, and is slidably mounted on the upstream backstop 64 of the supporting part 66 on intermediate along axle 18 extruding.Preferably, upstream backstop 64 extrudes the shoulder 68 of intermediate 22.Second spring 60b pushes upstream backstop 64 equally against shoulder 68, and thus, the slack position of this spring even shown in its Fig. 2 a is applied in prestressing force.
In addition, moveable element 28 have flange shape, be intended to only from the degree of displacement of the restriction of element 28 and the degree of displacement exceeding the restriction of element 28 to contact the additional support members 70 of the block 64 of supporting part 66, specific descriptions will provide hereinafter.Same in operating position, between flange 70 and upstream backstop 64, there is axial clearance 74.
In fuel metering equipment 10, the first spring 60a of the first embodiment is positioned at the downstream of the second spring 60b.In addition, the first spring 60a is than the axle 18 of the second spring 60b closer to metering equipment 10.
The difference of the embodiment shown in the embodiment shown in Fig. 3 a to 3c and Fig. 2 a to 2c is in metering equipment 10, and the first spring 60a is positioned at the upstream of the second spring 60b.In addition, the second spring 60b is than the axle 18 of the first spring 60a closer to metering equipment 10.
In fig. 3 a, the first spring 60a mono-aspect extrudes the edge 282 of moveable element 28, on the other hand the upstream shoulder 223 of the downstream hollow article 220 of extruded hollow intermediate 22.
The second spring 60b of the second embodiment is provided between the fixed stop 63 of equipment 10 and the supporting part 66 of movable seal element 28, and movable seal element 28 has the joint element 72 for engaging support members 66.
Joint element 72 for the mode of the additional support members 70 to be similar to the first embodiment along the direction of the maximum open position of movable seal element 28 with only from the degree of displacement limited and the degree of displacement exceeding restriction carrys out engaging support members 66.
In fig. 3 a, movable seal element 28 comprises piston 280 and supporting part 66.Piston 280 comprises joint element 72.In order to make moveable element 28 allow the fuel from opening 24 to arrive the second outlet 10b when exceeding the degree of displacement of restriction of element 28, gap 74 is provided at (as shown in Figure 3 a) between joint element 72 and supporting part 66.
The supporting part 66 of the second embodiment is safety valve, valve rod more precisely.Safety valve 66 is arranged to the downstream shoulder 222 engaging downstream hollow article 220 hermetically.In metering equipment 10, downstream shoulder 222 is especially positioned at the downstream of upstream shoulder 223.
Similarly, the second spring 60b pushes safety valve 66 and is pressed against shoulder 222, and therefore this spring 60b is even applied in prestressing force in the release position shown in its Fig. 3 a.
Joint element 72 is the undercuts formed in piston 280, and the valve rod of safety valve 66 especially can engage as the block in maximum open position further groove 72.
With reference to Fig. 2 a to 2c and Fig. 3 a to 3c, the operation of metering equipment 10 is described.
If the pressure difference between the upstream and downstream of equipment 10 does not exceed threshold values, element 28 is retained in operating position as shown by figures 2 a and 3.In other words, the restoring force that first spring 60a applies is enough to holding member 28 and is pushed to its valve seat 26, this power be greater than the power caused by the pressure difference between being applied in the fuel pressure of the upstream pressure-bearing surface of extrusion element 28 fuel pressure equal with the power of the fuel contacted with the downstream of element 28 substantially in firing chamber really.
Preferably, the sealing provided by the moveable element in operating position can remain to the situation that pressure difference is approximately 3.5 bar.
When this pressure difference increases, cause making a concerted effort on element 28 element 28 to cause spring 60a, and be therefore displaced to maximum open position from its operating position.The beginning of this displacement illustrated in Fig. 2 b and 3b, this is displaced through Compress Spring 60a to realize, element 28 release opening 24 and start the first fuel circuit.Then, the fuel from storage tank really can be successfully carried through opening 24, be passed aperture 32, the annular space 30 of intermediate 22 for fuel, then through the first outlet 10a before arrival first loop 12.In the first stage of the carrying out of this moveable element 28, only have the first spring 60a to be compressed, along with element is shifted on downstream direction, gap 74 is progressively filled.Still during this first stage, the second opening 46 is still closed through the second opening 46 by the downstream of element 28 50 simultaneously, stops fuel to pass through to go to and reach inactive second servo loop with this.
Only have when moveable element 28 has reached the degree of displacement of restriction on downstream direction, the second servo loop of sparger just can start.When the part 54 of the narrowing section of element arrives the position relative with the second opening 46, obtain this degree of displacement limited reached in the intermediate configurations between these configurations shown in Fig. 2 a, 3b, 2c and 3c, the space produced between the wall and the outer surface of element of this opening allows fuel to pass through.In order to the object of information, can be that there is the part 54 for the axial groove at interval circumferentially each other making fuel pass through here.In addition, these grooves can be axioversions with in the upstream direction close to axle 18, like this because element 28 just adds flow velocity by fuel to downstream shift.Therefore, equipment 10 provides and depends on the accurate function of measuring of element 28 along the degree of displacement of axle 18.In this respect, notice that Fig. 2 c shows the moveable element 28 in the maximum open position allowing the maximum fuel flowing velocity obtaining sparger outlet port.
As long as element 28 1 reaches its degree of displacement (such as reaching the pressure difference of about 7 bar) limited, fuel from storage tank just successfully can flow through fuel inlet aperture 42, cavity 40, fuel outlet aperture 44, second opening 46, then through leading to second space 56 exporting 10b of circulating with the second servo loop 14 of sparger.Fuel is in the second loop with these high-caliber flowing velocity flowings, and owing to being still through a part of fuel supply of opening 24 by the aperture 32 of intermediate 22 for fuel, fuel also will continue to flow in the first loop.
More specifically, with reference to Fig. 2 a to 2c, after the block 64 being pressed against slide member 66 by crush ribs 70 by flange 70 at the second spring 60b is initiated, reach the degree of displacement of the restriction of element.
In a second embodiment, behind the gap 74 between the bottom of the groove 72 in the valve stem end of filling safety valve 66 at least in part and piston 280, by engaging by piston the degree of displacement limited that safety valve 66 reaches movable seal element 28.
More generally, in order to reach the degree of displacement in the first and second embodiments, element must resist by each restoring force produced in two of arranged in parallel springs 60a, 60b.In the beginning of compression second spring 60b, or (in this traveling process, two springs are initiated in a parallel fashion) can reach the degree of displacement of the restriction corresponding with the circulation degree of metering equipment after element is advanced.
Certainly, those skilled in the art can make various change by nonrestrictive example to described the present invention.

Claims (9)

1. the fuel metering equipment (10) for the fuel injector of aircraft turbine machine, described equipment comprises for the opening (24) of fuel picked-up, for sealing the moveable element (28) of described opening and being designed to recover the elastic recovery device (60a of described seal element (28) on the direction of the operating position at opening place described in described component seal, 60b), described element (28) is designed to be shifted from its operating position under the effect being applied to the fuel pressure on this element;
Wherein, described metering equipment (10) comprise be intended to carry out circulating with the primary circuit of described sparger (12) first export (10a) and second exporting (10b) of being intended to carry out circulating with the second servo loop of described sparger (14);
Wherein, described metering equipment (10) is designed to the degree of displacement of the restriction reaching described seal element (28) on the direction of maximum open position, and described seal element allows the fuel from described opening (24) to arrive described first outlet (10a); And
Wherein, only exceed the degree of displacement of the described restriction of described seal element (28), described seal element (28) just allows the described fuel from described opening (24) to arrive described second outlet (10b);
It is characterized in that, described metering equipment (10) comprising:
Hollow ectosome (20);
Be contained in the hollow intermediate (22) in described ectosome (20), described opening (24) is configured in the described intermediate of the valve seat (26) had for holding described seal element (28);
Be contained in the described seal element (28) of movement slidably in described intermediate (22);
Be provided in described intermediate and ectosome (22,20) the fuel flowing space (30) between, described intermediate to have for fuel from the inside of this intermediate (22) through the aperture (32) reaching the described fuel flowing space (30), and the described flowing space and described first exports (10a) and circulates;
Be provided in the second opening (46) passed for described fuel on described intermediate (22), if the degree of displacement that described second opening is intended to not reach described restriction is just sealed by described moveable element (28), and described second opening is intended to be released when described moveable element (28) is between the degree of displacement limited and its maximum open position, and described second opening (46) and described second exports (10b) and circulates.
2. equipment according to claim 1, it is characterized in that, when exceeding the degree of displacement of described restriction of described seal element (28), described seal element (28) allows the fuel from described opening (24) to arrive described second outlet (10b) and described first outlet (10a).
3. equipment according to claim 1 and 2, it is characterized in that, described elastic recovery device comprises at least one first spring (60a) and the second spring (60b), described second spring is not initiated by the stroke at least partially of arranging as the described seal element (28) the operating position from described seal element (28), and described first and second spring (60a, 60b) by arrangement be when described seal element (28) is in the degree of displacement of described restriction, each spring is caused by described seal element (28), and described first and second spring (60a, 60b) be preferably arranged in parallel.
4. equipment according to claim 3, it is characterized in that, described second spring (60b) is provided between the block (62) of described intermediate and supporting part (66), and described moveable seal element (28) have to be intended on the direction of the maximum open position of described seal element only from the degree of displacement of described restriction and the degree of displacement exceeding described restriction to contact the extra supporting part (70) of described supporting part (66).
5. equipment according to claim 3, it is characterized in that, described second spring (60b) is provided between the fixed stop (63) of described equipment (10) and the supporting part (66) of described moveable seal element (28), described moveable seal element (28) to have on the direction of the maximum open position described movable seal element (28) only from the degree of displacement of described restriction and the degree of displacement exceeding described restriction to engage the joint element (72) of described supporting part (66).
6. according to equipment in any one of the preceding claims wherein, it is characterized in that, described moveable parts (28) define cavity (40), and described fuel is intended to conveying in described cavity (40) to arrive described second outlet (10b).
7. the fuel injector for aircraft turbine machine (1), comprise according at least one metering equipment (10) in any one of the preceding claims wherein, described first outlet (10a) is circulated with the primary circuit (12) of described sparger, and described second outlet (10b) is circulated with the second servo loop (14) of described sparger.
8. an aircraft turbine machine firing chamber, comprises multiple fuel injector according to claim 7 (1).
9. an aircraft turbine machine, comprises firing chamber according to claim 8.
CN201480012251.XA 2013-03-05 2014-03-05 Compact dosing device for the ejector with two fuel circuits of aircraft turbine machine Active CN105026732B (en)

Applications Claiming Priority (5)

Application Number Priority Date Filing Date Title
FR1351946 2013-03-05
FR1351946A FR3003013B1 (en) 2013-03-05 2013-03-05 COMPACT DOSING DEVICE FOR TWO FUEL CIRCUIT INJECTOR, PREFERABLY FOR AIRCRAFT TURBOMACHINE
FR1360197 2013-10-18
FR1360197A FR3003014B1 (en) 2013-03-05 2013-10-18 COMPACT DOSING DEVICE FOR TWO FUEL CIRCUIT INJECTOR, PREFERABLY FOR AIRCRAFT TURBOMACHINE
PCT/FR2014/050499 WO2014135797A1 (en) 2013-03-05 2014-03-05 Compact dosing device for an injector with two fuel circuits for an aircraft turbomachine

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CN105026732A true CN105026732A (en) 2015-11-04
CN105026732B CN105026732B (en) 2017-03-08

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EP (1) EP2964933B1 (en)
CN (1) CN105026732B (en)
CA (1) CA2904481C (en)
FR (2) FR3003013B1 (en)
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WO (1) WO2014135797A1 (en)

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EP2964933B1 (en) 2018-05-30
CN105026732B (en) 2017-03-08
CA2904481C (en) 2020-12-01
FR3003014A1 (en) 2014-09-12
RU2646666C2 (en) 2018-03-06
FR3003013B1 (en) 2016-07-29
WO2014135797A1 (en) 2014-09-12
RU2015142055A (en) 2017-04-07
FR3003013A1 (en) 2014-09-12
CA2904481A1 (en) 2014-09-12
US10041411B2 (en) 2018-08-07
FR3003014B1 (en) 2016-07-29
BR112015020995A2 (en) 2017-07-18
EP2964933A1 (en) 2016-01-13
US20160017808A1 (en) 2016-01-21

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